Rotary manifold for a cohesion-type drive

ABSTRACT

A rotary manifold for a rotor assembly of a cohesion-type drive includes a manifold body extending along a drive axis for rotation thereabout, a first ductwork internal the body for fluid communication with a plurality of first chambers of the drive, and a second ductwork internal the body for fluid communication with a plurality of second chambers of the drive. The second ductwork is in fluid isolation of the first ductwork.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of U.S. application Ser. No.16/943,683, filed Jul. 30, 2020, which is a divisional of U.S. patentapplication Ser. No. 15/821,808, filed on Nov. 23, 2017, and issued asU.S. Pat. No. 10,794,239, which claims the benefit of U.S. ProvisionalApplication No. 62/426,109, filed on Nov. 23, 2016 and of U.S.Provisional Application No. 62/426,122, filed on Nov. 23, 2016, each ofwhich is hereby incorporated herein by reference in its entirety.

FIELD

The disclosure relates to cohesion-type drives. More specifically, thedisclosure relates to manifolds for rotor assemblies of cohesion-typedrives.

BACKGROUND

U.S. Pat. No. 3,899,875 (Oklejas et al.) discloses a gas turbine. Theturbine comprises a casing and a rotor mounted on bearings within thecasing. The rotor is of a Tesla-type configuration. Means are providedon the rotor to conduct cooling air to alternate spaces between sets ofdisc-like blades of the rotor and to conduct a working fluid to oppositealternate spaces between the blades. The air cools the blades and iscorrespondingly heated. A collecting chamber receives the heated air andconducts it ultimately to a combustion chamber.

U.S. Pat. No. 3,999,377 (Oklejas et al.) discloses a tesla-type turbineincluding turbine blade cooling means. The turbine blades define aplurality of alternate spaces, with an air-conducting cooling spacepositioned between each pair of turbine or working spaces. While hotworking gas expands between blades in the turbine spaces, cooling airflows in the opposite direction in the adjacent cooling spaces to coolthe turbine blades. The disclosed turbine construction provides foraxial air inflow and radial air outflow, with axial exhaust of workinggas. After being heated by contact with the turbine blades, the coolingair is utilized in the combustion chamber of the turbine.

U.S. Pat. No. 3,007,311 (Amero) discloses an apparatus including aplurality of spaced discs coaxially positioned on a hub and securedagainst rotation about the hub, such discs defining a series of spacesextending along the hub, and a pair of isolated passageways axiallydisposed in the hub having alternate radial communication with theseries of spaces, one of such passageways constituting an intakemanifold and the other of such passageways constituting the exhaustmanifold.

SUMMARY

The following summary is intended to introduce the reader to variousaspects of the applicant's teaching, but not to define any invention.

According to some aspects, a cohesion-type drive includes (a) a casing;(b) a shaft rotatably supported in the casing for rotation about a driveaxis in a circumferential forward direction; and (c) a disc packsupported in the casing coaxial with the shaft and fixed to rotatetherewith. The disc pack includes a plurality of discs spaced axiallyapart from one another by disc spaces. The disc spaces include aplurality of compression chambers and a plurality of turbine chambers,with the turbine chambers alternating axially with and in fluidisolation of the compression chambers. The drive further includes (d) ahub manifold in the casing radially inward of the disc pack and fixed torotate with the shaft about the drive axis. The hub manifold includes ahub body coaxial with the drive axis, a compression chamber inletductwork internal the hub body and in fluid communication with thecompression chambers for conducting a first fluid into the compressionchambers to compress the first fluid during rotation of the disc pack inthe forward direction, and a turbine chamber outlet ductwork internalthe hub body and in fluid communication with the turbine chambers forevacuating a second fluid from the turbine chambers. The turbine chamberoutlet ductwork is in fluid isolation of the compression chamber inletductwork. The drive further includes a shroud manifold in the casingradially outward of the disc pack. The shroud manifold includes acompression chamber outlet ductwork in fluid communication with thecompression chambers for evacuating the first fluid from the compressionchambers, and a turbine chamber inlet ductwork in fluid communicationwith the turbine chambers for conducting the second fluid into theturbine chambers to urge rotation of the disc pack in the forwarddirection. The turbine chamber inlet ductwork in fluid isolation of thecompression chamber outlet ductwork.

In some examples, the hub body includes a body first endface, a bodysecond endface axially opposite the body first endface, and a body outersurface extending between the body first and second endfaces anddirected radially outwardly toward the disc pack. The disc spaces arebounded radially by the body outer surface. The compression chamberinlet ductwork includes a plurality of compression chamber inlet portsopen to the body outer surface for discharging the first fluid from thecompression chamber inlet ductwork into the compression chambers, andthe turbine chamber outlet ductwork includes a plurality of turbinechamber outlet ports open to the body outer surface for evacuating thesecond fluid from the turbine chambers and into the turbine chamberoutlet ductwork.

In some examples, the compression chamber inlet ductwork includes aplurality of circumferentially spaced apart headers in fluidcommunication with the compression chamber inlet ports. Each headerextends along a header centerline between a header first end open to thebody first endface for receiving the first fluid and a header second endspaced axially apart from the header first end toward the body secondendface.

In some examples, the header centerline extends helically about thedrive axis in the circumferential forward direction from the headerfirst end to the header second end.

In some examples, each header has a cross sectional area perpendicularto the drive axis, and the cross-sectional area of each header decreasesalong the header centerline from the header first end toward the headersecond end.

In some examples, the hub manifold includes a plurality of aerodynamicfeatures extending at least partially across the header first ends andfixed to rotate with the hub body for conditioning flow of the firstfluid entering the header first ends. In some examples, the aerodynamicfeatures comprise circumferentially spaced apart airfoils extendingradially across respective header first ends.

In some examples, the compression chamber inlet ductwork includes aplurality of inlet conduits for conducting the first fluid from theheaders to the compression chamber inlet ports, and each inlet conduitextends along an inlet conduit centerline between a respectivecompression chamber inlet port and an inlet conduit intake end open to arespective header.

In some examples, the inlet conduit centerline curves circumferentiallybetween the chamber inlet port and the inlet conduit intake end. In someexamples, the inlet conduit centerline extends from the inlet conduitintake end to the compression chamber inlet port in a circumferentialreverse direction opposite the forward direction for directing fluidpassing radially outwardly through the inlet conduit and into arespective compression chamber in the reverse direction.

In some examples, the hub body includes a body inner surface radiallyopposite the body outer surface, and a manifold bore coaxial with thedrive axis and bounded radially by the body inner surface. In someexamples, the turbine chamber outlet ductwork includes a plurality ofoutlet conduits for conducting the second fluid from the turbine chamberoutlet ports to a fluid evacuation space provided in the manifold bore.Each outlet conduit extends along an outlet conduit centerline between arespective turbine chamber outlet port and an outlet conduit dischargeend open to the body inner surface and in fluid communication with theevacuation space.

In some examples, the outlet conduit centerline curves circumferentiallybetween the turbine chamber outlet port and the outlet conduit dischargeend. In some examples, the outlet conduit centerline extends from theturbine chamber outlet port to the outlet conduit discharge end in thecircumferential forward direction for directing the second fluid passingradially inwardly through the outlet conduit in the forward direction.

In some examples, compression chamber inlet ports are arranged inaxially spaced apart inlet sets, and the compression chamber inlet portsin each set are spaced circumferentially apart from one another aboutthe drive axis and open to a respective compression chamber. In someexamples, the turbine chamber outlet ports are arranged in axiallyspaced apart outlet sets alternating axially with the inlet sets, andthe turbine chamber outlet ports in each set are spacedcircumferentially apart from one another about the drive axis and opento a respective turbine chamber.

In some examples, the hub manifold includes a plurality of axiallyspaced apart circumferential grooves in the hub body outer surface, eachgroove receiving a radially inner peripheral edge of a respective disc.

In some examples, the body outer surface is spaced radially apart fromthe drive axis by a radius, the radius decreasing along the drive axisfrom the body first endface to the body second endface.

In some examples, the hub body includes a core coaxial with the driveaxis and through which at least a portion of the compression chamberinlet ductwork and the turbine chamber outlet ductwork passes, and aframe mounted to the core for exerting an inwardly directed force on thecore to regulate a stress distribution therein during operation.

In some examples, the core has a radially outwardly directed core outersurface, and the frame includes an outer sleeve mounted over the coreand in engagement with the core outer surface for inducing radialcompression of the core during operation.

In some examples, the core includes a radially inwardly directed coreinner surface radially opposite the core outer surface, and a core borecoaxial with the drive axis and bounded radially by the core innersurface, and the frame includes an inner sleeve in the core bore and inengagement with the core inner surface. The inner and outer sleeves areanchored to one another for inducing radial compression of the coreduring operation.

In some examples, the core has a core first endface and a core secondendface axially opposite the core first endface, and the frame includesa first end cap in engagement with the core first endface and a secondend cap in engagement with the core second endface. The first and secondend caps are anchored to one another for inducing axial compression ofthe core during operation.

In some examples, at least a portion of the hub body is formed of athermally conductive material for conductively transferring heat betweenthe first fluid passing through the compression chamber inlet ductworkand the second fluid passing through the turbine chamber outletductwork.

In some examples, the shroud manifold is fixed to rotate with the shaftabout the drive axis, and includes a shroud body coaxial with the driveaxis, and the turbine chamber inlet ductwork and the compression chamberoutlet ductwork are internal the shroud body.

According to some aspects, a cohesion-type drive includes (a) a casing;(b) a shaft rotatably supported in the casing for rotation about a driveaxis in a circumferential forward direction; and (c) a disc packsupported in the casing coaxial with the shaft and fixed to rotatetherewith. The disc pack includes a plurality of discs spaced axiallyapart from one another by disc spaces. The disc spaces comprise aplurality of compression chambers and a plurality of turbine chambers,with the turbine chambers alternating axially with and in fluidisolation of the compression chambers. The drive further includes (d) ahub manifold in the casing radially inward of the disc pack. The hubmanifold includes a compression chamber inlet ductwork in fluidcommunication with the compression chambers for conducting a first fluidinto the compression chambers to compress the first fluid duringrotation of the disc pack in the forward direction, and a turbinechamber outlet ductwork in fluid communication with the turbine chambersfor evacuating a second fluid from the turbine chambers. The turbinechamber outlet ductwork is in fluid isolation of the compression chamberinlet ductwork. The drive further includes (e) a shroud manifold in thecasing radially outward of the disc pack and fixed to rotate with theshaft about the drive axis. The shroud manifold includes: a shroud bodycoaxial with the drive axis, a compression chamber outlet ductworkinternal the shroud body and in fluid communication with the compressionchambers for evacuating the first fluid from the compression chambers,and a turbine chamber inlet ductwork internal the shroud body and influid communication with the turbine chambers for conducting the secondfluid into the turbine chambers to urge rotation of the disc pack in theforward direction. The turbine chamber inlet ductwork is in fluidisolation of the compression chamber outlet ductwork.

In some examples, the shroud body includes a body first endface, a bodysecond endface axially opposite the body first endface, and a body innersurface extending between the first and second endfaces and directedradially inwardly toward the disc pack. The disc spaces are boundedradially by the body inner surface. The compression chamber outletductwork includes a plurality of compression chamber outlet ports opento the body inner surface for evacuating the first fluid from thecompression chambers and into the compression chamber inlet ductwork,and the turbine chamber inlet ductwork includes a plurality of turbinechamber inlet ports open to the body inner surface for discharging thesecond fluid from the turbine chamber outlet ductwork and into theturbine chambers to urge rotation of the disc pack in the forwarddirection.

In some examples, the turbine chamber inlet ductwork includes aplurality of circumferentially spaced apart headers in fluidcommunication with the turbine chamber inlet ports. Each header extendsbetween a header first end open to the body first endface for receivingthe second fluid and a header second end spaced axially apart from theheader first end toward the body second endface.

In some examples, the shroud manifold includes a plurality ofaerodynamic features extending at least partially across the headerfirst ends and fixed to rotate with the shroud body for conditioningflow of the second fluid entering the headers.

In some examples, the aerodynamic features include circumferentiallyspaced apart airfoils extending radially across respective header firstends.

In some examples, the turbine chamber inlet ductwork includes aplurality of inlet conduits for conducting the second fluid from theheaders to the turbine chamber inlet ports, and each inlet conduitextends along an inlet conduit centerline between a respective turbinechamber inlet port and an inlet conduit intake end open to a respectiveheader.

In some examples, the inlet conduit centerline curves circumferentiallybetween the turbine chamber inlet port and the inlet conduit intake end.In some examples, the inlet conduit centerline extends from the inletconduit intake end to the turbine chamber inlet port in thecircumferential forward direction for directing fluid passing radiallyinwardly through the inlet conduit and into the turbine chamber in theforward direction.

In some examples, the shroud body has a body outer surface radiallyopposite the body inner surface, and the drive includes a fluidevacuation space in the casing radially intermediate the shroud manifoldand an inner surface of the casing and bounded radially by the bodyouter surface for evacuating the first fluid. The compression chamberoutlet ductwork includes a plurality of outlet conduits for conductingthe first fluid from the compression chamber outlet ports to theevacuation space, and each outlet conduit extends along an outletconduit centerline between a respective compression chamber outlet portand an outlet conduit discharge end open to the body outer surface andin fluid communication with the evacuation space.

In some examples, the outlet conduit centerline curves circumferentiallybetween the compression chamber outlet port and the outlet conduitdischarge end. In some examples, the outlet conduit includes an intakeportion extending along an intake portion centerline from thecompression chamber outlet port toward the outlet conduit discharge end.The intake portion centerline extends from the compression chamberoutlet port toward the outlet conduit discharge end in a circumferentialreverse direction opposite the forward direction for directing the firstfluid entering and passing radially outwardly through the intake portionin the reverse direction.

In some examples, the outlet conduit includes a discharge portionextending along a discharge portion centerline from the intake portionto the outlet conduit discharge end, the discharge portion centerlineextending from the intake portion to the outlet conduit discharge end inone of the circumferential forward direction and the reverse directionfor directing the first fluid passing radially outwardly through thedischarge portion and into the evacuation space in the one of theforward and reverse direction.

In some examples, the turbine chamber inlet ports are arranged inaxially spaced apart inlet sets. The turbine chamber inlet ports in eachset are spaced circumferentially apart from one another about the driveaxis and open to a respective turbine chamber. The compression chamberoutlet ports are arranged in axially spaced apart outlet setsalternating axially with the inlet sets. The compression chamber outletports in each set are spaced circumferentially apart from one anotherabout the drive axis and open to a respective compression chamber.

In some examples, the shroud manifold includes a plurality of axiallyspaced apart circumferential grooves in the shroud body inner surface,each groove receiving a radially outer peripheral edge of a respectivedisc.

According to some aspects, a manifold for a rotor assembly of acohesion-type drive includes (a) a manifold body extending along a driveaxis for rotation thereabout in a circumferential first direction, (b) afirst ductwork internal the body for fluid communication with aplurality of first chambers of the drive, and (c) a second ductworkinternal the body for fluid communication with a plurality of secondchambers of the drive, the second ductwork in fluid isolation of thefirst ductwork.

In some examples, the body includes a first endface, a second endfaceaxially opposite the first endface, a radially outwardly directed bodyouter surface extending between the first and second endfaces, aradially inwardly directed body inner surface radially opposite the bodyouter surface and extending between the first and second endfaces, and amanifold bore in the body coaxial with the drive axis and boundedradially by the body inner surface.

In some examples, the first ductwork includes a plurality of first portsopen to one of the body inner surface and the body outer surface forconducting fluid between the first ductwork and the first chambers. Insome examples, the first ports are arranged in a plurality of axiallyspaced apart first sets, and each first set is arranged for fluidcommunication with a respective first chamber.

In some examples, the second ductwork includes a plurality of secondports open to the one of the body inner surface and the body outersurface for conducting fluid between the second ductwork and the secondchambers. In some examples, the second ports are arranged in a pluralityof axially spaced apart second sets, and the second sets alternateaxially with the first sets. Each second set is arranged for fluidcommunication with a respective second chamber.

In some examples, the first ports in each set are spacedcircumferentially apart from one another about the drive axis, and thesecond ports in each set are spaced circumferentially apart from oneanother about the drive axis.

In some examples, the first ports in each set lie in a common firstplane oriented normal to the drive axis, and the second ports in eachset lie in a common second plane oriented normal to the drive axis.

In some examples, the first ductwork includes a plurality ofcircumferentially spaced apart headers in fluid communication with thefirst ports. Each header extends along a header centerline between aheader first end open to the body first endface for receiving fluid anda header second end spaced axially apart from the header first endtoward the body second endface.

In some examples, the header centerline extends helically about thedrive axis in the circumferential first direction from the header firstend to the header second end.

In some examples, each header has a cross sectional area perpendicularto the drive axis. The cross-sectional area of each header decreasesalong the header centerline from the header first end toward the headersecond end.

In some examples, the manifold includes a plurality of aerodynamicfeatures extending at least partially across the header first ends andfixed to rotate with the body for conditioning flow of fluid enteringthe header first ends.

In some examples, the aerodynamic features comprise circumferentiallyspaced apart airfoils extending radially across respective header firstends.

In some examples, the first ductwork includes a plurality of firstconduits for conducting fluid between the headers and the first ports.Each first conduit extends along a first conduit centerline between arespective first port and a first conduit end open to a respectiveheader. In some examples, the first conduit centerline curvescircumferentially between the first port and the first conduit end.

In some examples, the first ports are open to the body outer surface andspaced radially outwardly from the first conduit ends, and each firstconduit centerline extends radially outwardly and in a circumferentialsecond direction opposite the first direction from a respective firstconduit end to a respective first port for directing fluid passingradially outwardly through the first conduit in the second direction.

In some examples, the first ports are open to the body inner surface andspaced radially inwardly from the first conduit ends, and each firstconduit centerline extends radially inwardly and in the circumferentialfirst direction from a respective first conduit end to a respectivefirst port for directing fluid passing radially inwardly through thefirst conduit in the first direction.

In some examples, the second ductwork includes a plurality of secondconduits. Each second conduit extends along a second conduit centerlinebetween a respective second port and a second conduit end open to theother one of the body inner surface and the body outer surface. In someexamples, the second conduits curve circumferentially between the secondport and the second conduit end.

In some examples, the second ports are open to the body outer surfaceand the second conduit ends are open to the body inner surface, andwherein each second conduit centerline extends radially inwardly and inthe circumferential first direction from a respective second port to arespective second conduit end for directing fluid passing radiallyinwardly through the second conduit in the first direction.

In some examples, the second ports are open to the body inner surfaceand the second conduit ends are open to the body outer surface, and eachsecond conduit includes an intake portion extending along an intakeportion centerline from a respective second port toward a respectivesecond conduit end. The intake portion centerline extends radiallyoutwardly and in a circumferential second direction opposite the firstdirection from the second port toward the conduit second end fordirecting fluid passing radially outwardly through the intake portion inthe second direction.

In some examples, the second conduit includes a discharge portionextending along a discharge portion centerline from the intake portionto the second conduit end. The discharge portion centerline extendsradially outwardly and in one of the circumferential first direction andthe second direction from the intake portion to the conduit second endfor directing fluid passing radially outwardly through the dischargeportion and out the conduit second end in the one of the first directionand the second direction.

In some examples, the manifold includes a plurality of axially spacedapart circumferential grooves in the one of the body inner surface andthe body outer surface for mounting a plurality of discs of the drive.Each groove is axially intermediate a respective first set of firstports and a respective axially adjacent second set of second ports, andeach groove configured for receiving a peripheral edge of a respectivedisc.

In some examples, the manifold includes an interference structure forengagement with a disc pack to rotationally lock the disc pack with themanifold.

In some examples, the body outer surface is spaced radially apart fromthe drive axis by a radius, and the radius decreases along the driveaxis from the body first endface to the body second endface.

In some examples, the body includes a core coaxial with the drive axisand through which at least a portion of the first ductwork and thesecond ductwork passes, and a frame mounted to the core for exerting aninwardly directed force on the core to regulate a stress distributiontherein during operation.

In some examples, the core has a radially outwardly directed core outersurface, and the frame includes an outer sleeve mounted over the coreand in engagement with the core outer surface for inducing radialcompression of the core during operation.

In some examples, the body includes a core bore in the core coaxial withthe drive axis and bounded by a radially inwardly directed core innersurface of the core, and the frame includes an inner sleeve in the corebore and in engagement with the core inner surface. The inner and outersleeves are anchored to one another for inducing radial compression ofthe core during operation.

In some examples, the core has a core first endface and a core secondendface axially opposite the core first endface, and the frame includesa first end cap in engagement with the core first endface and a secondend cap in engagement with the core second endface. The first and secondend caps anchored to one another for inducing axial compression of thecore during operation.

In some examples, at least a portion of the body is formed of athermally conductive material for transferring heat between fluidpassing through the first ductwork and fluid passing through the secondductwork.

According to some aspects, a manifold for a rotor assembly of acohesion-type drive includes (a) a manifold body extending along a driveaxis for rotation thereabout, and (b) ductwork internal the body forfluid communication with a plurality of working chambers of the drive.

In some examples, the body includes a first endface, a second endfaceaxially opposite the first endface, a radially outwardly directed bodyouter surface extending between the first and second endfaces, aradially inwardly directed body inner surface radially opposite the bodyouter surface and extending between the first and second endfaces, and amanifold bore in the body coaxial with the drive axis and boundedradially by the body inner surface.

In some examples, the ductwork includes a plurality of ports open to oneof the body inner surface and the body outer surface for conductingfluid between the ductwork and the chambers. In some examples, the portsare arranged in a plurality of axially spaced apart sets, and each setis arranged for fluid communication with a respective chamber.

In some examples, the manifold comprises a shroud manifold forpositioning radially outward of a disc pack of the drive, and the portsare open to the body inner surface.

In some examples, the manifold comprises a hub manifold for positioningradially inward of a disc pack of the drive, and the ports are open tothe body outer surface.

In some examples, the ductwork includes a plurality of conduits, eachconduit extending between a respective port and a conduit end. In someexamples, the conduits are curved circumferentially between the port andthe conduit end.

In some examples, the ductwork includes a plurality of headers extendinginto the body from the first endface and in fluid communication with theports. The headers are spaced circumferentially apart from one anotherabout the drive axis.

According to some aspects, a manifold for a rotor assembly of acohesion-type drive includes: (a) a manifold body extending along adrive axis for rotation thereabout. The body includes a core coaxialwith the drive axis, and a frame mounted to the core for exerting aninwardly directed force on the core to regulate a stress distributiontherein during operation of the drive. The manifold further includes (b)a first ductwork internal the body for fluid communication with aplurality of working chambers of the drive. At least a portion of theductwork passes through the core.

In some examples, the core has a radially outwardly directed core outersurface, and the frame includes an outer sleeve mounted over the coreand in engagement with the core outer surface for inducing radialcompression of the core during operation.

In some examples, the body includes a core bore in the core coaxial withthe drive axis and bounded by a radially inwardly directed core innersurface of the core, and the frame includes an inner sleeve in the corebore and in engagement with the core inner surface. The inner and outersleeves are anchored to one another for inducing radial compression ofthe core during operation.

In some examples, the frame includes a plurality of anchors anchoringthe inner and outer sleeves to one another. Each anchor extends betweenan anchor outer end fixed to the outer sleeve and an anchor inner endfixed to the inner sleeve.

In some examples, the manifold body includes a plurality of aperturespassing radially through the core between the core inner and outersurfaces, and the anchors extend through respective apertures.

In some examples, the core has a core first endface and a core secondendface axially opposite the core first endface, and the frame includesa first end cap in engagement with the core first endface and a secondend cap in engagement with the core second endface. The first and secondend caps are anchored to one another for inducing axial compression ofthe core during operation.

In some examples, the frame includes a disc pack mounting portion forengagement with the disc pack to fix the disc pack to the frame, a shaftmounting portion spaced radially inwardly from the disc pack mountingportion for engagement with the shaft to fix the shaft to the frame, andone or more torque-transfer members for transferring torque between thedisc pack mounting portion and the shaft mounting portion. Eachtorque-transfer member has a radially outer end fixed to the disc packmounting portion and a radially inner end fixed to the shaft mountingportion.

BRIEF DESCRIPTION OF THE DRAWINGS

The drawings included herewith are for illustrating various examples ofapparatuses and methods of the present specification and are notintended to limit the scope of what is taught in any way. In thedrawings:

FIG. 1 is a front perspective view of an example cohesion-type drive;

FIG. 2 is a cross-sectional view of portions of the drive of FIG. 1 ,taken along line 2-2 of FIG. 1 ;

FIG. 2A is an enlarged portion of FIG. 2 , showing front portions of ashroud manifold of the drive of FIG. 1 ;

FIG. 2B is another enlarged portion of FIG. 2 , showing front portionsof a hub manifold of the drive of FIG. 1 ;

FIG. 2C is another enlarged portion of FIG. 2 , showing rear portions ofthe shroud manifold;

FIG. 2D is another enlarged portion of FIG. 2 , showing rear portions ofthe hub manifold;

FIG. 3 is a simplified schematic representation of an upper half of FIG.2 ;

FIG. 4 is a cross-sectional view of portions of the drive of FIG. 1 ,taken along line 4-4 of FIG. 2 ;

FIG. 4A is an enlarged portion of FIG. 4 , showing a portion of theshroud manifold;

FIG. 4B is another enlarged portion of FIG. 4 , showing the hubmanifold;

FIG. 5 is a cross-sectional view of portions of the drive of FIG. 1 ,taken along line 5-5 of FIG. 2 ;

FIG. 5A is an enlarged portion of FIG. 5 , showing a portion of theshroud manifold;

FIG. 5B is another enlarged portion of FIG. 5 , showing the hubmanifold;

FIG. 6A is a front perspective cut-away view of a portion of the hubmanifold, showing an internal hub ductwork arrangement of the hubmanifold;

FIG. 6B is a front perspective cut-away view of another portion of thehub manifold, showing another internal hub ductwork arrangement of thehub manifold;

FIG. 6C is a side view of an upper portion of the hub manifold;

FIG. 7A is a front perspective cut-away view of a portion of the shroudmanifold, showing an internal shroud ductwork arrangement of the shroudmanifold;

FIG. 7B is a front perspective cut-away view of another portion of theshroud manifold, showing another internal shroud ductwork arrangement ofthe shroud manifold;

FIG. 8 is an exploded view of portions of a hub manifold structure and adisc pack of the drive of FIG. 1 ;

FIG. 9A is a front perspective partial cut-away view of a portion ofanother hub manifold for a drive like that of FIG. 1 , showing portionsof an internal hub ductwork arrangement of the hub manifold;

FIG. 9B is a front perspective partial cut-away view of another portionof hub manifold of FIG. 9A, showing portions of another internal hubductwork arrangement of the hub manifold;

FIG. 10 is a simplified schematic representation of portions of anothercohesion-type drive;

FIG. 11 is a simplified schematic representation of another hub manifoldfor a drive like that of FIG. 1 ; and

FIG. 12 includes charts and a table showing the difference in stressdistribution for a hollow rotating disc with and without imposed radialloads at the inner and outer radiuses.

DETAILED DESCRIPTION

Various apparatuses or processes will be described below to provide anexample of an embodiment of each claimed invention. No embodimentdescribed below limits any claimed invention and any claimed inventionmay cover processes or apparatuses that differ from those describedbelow. The claimed inventions are not limited to apparatuses orprocesses having all of the features of any one apparatus or processdescribed below or to features common to multiple or all of theapparatuses described below. It is possible that an apparatus or processdescribed below is not an embodiment of any claimed invention. Anyinvention disclosed in an apparatus or process described below that isnot claimed in this document may be the subject matter of anotherprotective instrument, for example, a continuing patent application, andthe applicants, inventors or owners do not intend to abandon, disclaimor dedicate to the public any such invention by its disclosure in thisdocument.

A cohesion-type drive includes a casing, a shaft rotatably supported inthe casing for rotation about a drive axis, and a disc pack coaxial withthe shaft and fixed to rotate therewith. The disc pack includes aplurality of coaxial discs that are spaced axially apart from oneanother by disc spaces forming a plurality of working chambers. Typicaldisc packs include annular discs, but some designs can include conicaldiscs, reverse flow discs, hybrid discs, etc.

In pump or compressor applications, the shaft is driven to rotate thediscs and a fluid is conducted into a radially inner portion of thechambers. The rotating discs impart work on the fluid and the fluid isurged radially outwardly. In turbine applications, a fluid is dischargedinto a radially outer portion of the chambers. The fluid imparts work onthe discs to drive rotation of the shaft in the circumferentialdirection and flows through the chambers radially inwardly.

In some examples, the disc spaces can include a plurality of firstchambers and a plurality of second chambers alternating axially with thefirst chambers. The first and second chambers can be in fluid isolationof one another. A first fluid can be conducted into the first chambersand a second fluid different from the first fluid can be conducted intothe second chambers.

In some examples, the first chambers can comprise one of compressionchambers and turbine chambers, and the second chambers can comprise theother one of compression chambers and turbine chambers. In suchexamples, the cohesion-type drive can operate as a regenerator incombination with a fluid power device. For example, the first chamberscan comprise compression chambers and a first fluid can be conductedinto a radially inner portion of the compression chambers forcompression thereof. The second chambers can comprise turbine chambersand a second fluid can be discharged into a radially outer portion ofthe second chambers to impart work on the disc pack for urging rotationof the shaft. The work imparted on the disc pack by the second fluid canbe greater than the work extracted from the disc pack by the firstfluid, thereby generating a net work output. In such examples, the firstfluid can include a relatively cool fluid, such as atmospheric air, andthe second fluid can include a relatively hot fluid, such as combustiongases. This can facilitate regenerative heat exchange across the discsas the first and second fluids pass through respective chambers, and canhelp cool the discs.

In some examples, after compression, the first fluid can be evacuatedfrom the first chambers and conducted to a combustion chamber. The firstfluid can be mixed with fuel and the mixture can be combusted togenerate the combustion gases for discharging into the second chambers.

Such cohesion-type drives as described above generally require manifoldsto conduct working fluid into and/or out from the working chambers, andthe manifold design can affect the performance of the drive. Accordingto some aspects of the teachings disclosed herein, design improvementscan advantageously be made to manifolds for such cohesion-type drives.

Referring to FIG. 1 , an example cohesion type drive 100 is illustrated.The drive 100 includes a casing 102 extending along a drive axis 104between a casing front end 106 and a casing rear end 108 spaced axiallyapart from the front end 106 in an axially rearward direction. A shaft110 is rotatably supported in the casing 102 for rotation about thedrive axis 104 in a circumferential first direction 112 (also referredto as forward direction 112).

Referring to FIG. 2 , in the example illustrated, a disc pack 114 issupported in the casing 102 coaxial with the shaft 110 and is fixed torotate therewith. Referring to FIG. 2A, the disc pack 114 includes aplurality of axially spaced apart discs 116. In the example illustrated,the discs 116 are generally annular.

Referring to FIG. 3 , in the example illustrated, the discs 116 arespaced axially apart from one another by disc spaces 118. The discspaces 118 define a plurality of compression chambers 120, and aplurality of turbine chambers 122 alternating axially with and in fluidisolation of the compression chambers 120.

Referring still to FIG. 3 , in the example illustrated, the drive 100further includes a first manifold 128 (also referred to as hub manifold128 or bore manifold 128) in the casing 102 radially inward of the discpack 114. The hub manifold 128 includes a hub first ductwork 130 (alsoreferred to as compression chamber inlet ductwork 130) for fluidcommunication with the compression chambers 120. The compression chamberinlet ductwork 130 is in fluid communication with the compressionchambers 120 for conducting a first fluid into the compression chambers120 to compress the first fluid during rotation of the disc pack 114 inthe forward direction 112. The first fluid can include, for example,air.

In the example illustrated, the hub manifold 128 includes a hub secondductwork 132 (also referred to as turbine chamber outlet ductwork 132)for fluid communication with the turbine chambers 122. In the exampleillustrated, the turbine chamber outlet ductwork 132 is in fluidcommunication with the turbine chambers 122 for evacuating a secondfluid from the turbine chambers 122. In the example illustrated, thesecond fluid has a temperature greater than the first fluid, and caninclude, for example, combustion gases. In the example illustrated, thecompression chamber inlet ductwork 130 and the turbine chamber outletductwork 132 are in fluid isolation of one another.

In the example illustrated, the drive 100 further includes a secondmanifold 138 (also referred to as shroud manifold 138) in the casing 102radially outward of the disc pack 114. In the example illustrated, theshroud manifold 138 includes a shroud first ductwork 140 (also referredto as a turbine chamber inlet ductwork 140) in fluid communication withthe turbine chambers 122. The turbine chamber inlet ductwork 140 is influid communication with the turbine chambers 122 for conducting thesecond fluid into the turbine chambers 122 to urge rotation of the discpack 114 in the forward direction 112. In the example illustrated, theshroud manifold 138 further includes a shroud second ductwork 142 (alsoreferred to as compression chamber outlet ductwork 142) in fluidcommunication with the compression chambers 120. The compression chamberoutlet ductwork 142 is in fluid communication with the compressionchambers 120 for evacuating the first fluid from the compressionchambers 120. In the example illustrated, the turbine chamber inletductwork 140 and the compression chamber outlet ductwork 142 are influid isolation of one another.

At least one of the hub manifold and the shroud manifold can be fixed torotate with the shaft about the drive axis. In the example illustrated,the hub manifold 128 is fixed to rotate with the shaft 110 about thedrive axis 104, and forms part of the rotor assembly of the drive 100.The hub manifold 128 includes a hub body 150 coaxial with the driveaxis, and each of the compression chamber inlet ductwork 130 and theturbine chamber outlet ductwork 132 are internal the hub body 150 (seealso FIGS. 6A, 6B). Providing the ductwork internal the manifold bodycan allow for optimization of the ductwork geometry to, for example,help condition fluid flow, minimize fluid losses, accommodate fluid flowfields at the manifold interfaces, control flow distribution among theworking chambers, and control heat transfer between fluids passingthrough the ductwork.

In the example illustrated, the hub body 150 is generally cylindrical.The hub body 150 includes a hub body first endface 150 a and a hub bodysecond endface 150 b axially opposite the hub body first endface 150 a.In the example illustrated, the hub body first endface 150 a is locatedtoward the casing front end 106, and the hub body second endface 150 bis spaced apart from the hub body first endface 150 a toward the casingrear end 108.

In the example illustrated, the hub body 150 includes a hub body outersurface 152 directed radially outwardly toward the disc pack 114 andextending axially between the hub body first and second endfaces 150 a,150 b. In the example illustrated, the disc spaces 118 are boundedradially by the hub body outer surface 152. The hub body 150 includes aradially inwardly directed hub body inner surface 154 radially oppositethe hub body outer surface 152 and extending axially between the hubbody first and second endfaces 150 a, 150 b. In the example illustrated,the hub manifold 128 includes a hub manifold bore 156 in the hub body150 coaxial with the drive axis 104, and bounded radially by the hubbody inner surface 154.

In the example illustrated, the compression chamber inlet ductwork 130includes a plurality of hub first ports 160 (also referred to ascompression chamber inlet ports 160) open to the hub body outer surface152 for discharging the first fluid from the compression chamber inletductwork 130 into the compression chambers 120. In the exampleillustrated, the turbine chamber outlet ductwork 132 includes aplurality of hub second ports 162 (also referred to as turbine chamberoutlet ports 162) open to the hub body outer surface 152 for evacuatingthe second fluid from the turbine chambers 122 and into the turbinechamber outlet ductwork 132.

Referring to FIG. 6C, in the example illustrated, the compressionchamber inlet ports 160 are arranged in axially spaced apart hub firstsets 160 a (also referred to as hub inlet sets 160 a), with each set 160a of compression chamber inlet ports 160 open to a respectivecompression chamber 120. In the example illustrated, the turbine chamberoutlet ports 162 are arranged in axially spaced apart hub second sets162 a (also referred to as hub outlet sets 162 a), with each set 162 aof turbine chamber outlet ports 162 open to a respective turbine chamber122. In the example illustrated, the hub outlet sets 162 a alternateaxially with the hub inlet sets 160 a.

Referring to FIG. 4B, in the example illustrated, the compressionchamber inlet ports 160 in each set 160 a are spaced circumferentiallyapart from one another about the drive axis 104. In the exampleillustrated, the compression chamber inlet ports 160 in each set 160 alie in a common hub first plane 163 a oriented normal to the drive axis104 (see also FIG. 6C). Referring to FIG. 5B, in the exampleillustrated, the turbine chamber outlet ports 162 in each set 162 a arespaced circumferentially apart from one another about the drive axis104. In the example illustrated, the turbine chamber outlet ports 162 ineach set 162 a lie in a common hub second plane 163 b normal to thedrive axis 104 (see also FIG. 6C).

Referring to FIG. 4B, in the example illustrated, the compressionchamber inlet ductwork 130 includes a plurality of circumferentiallyspaced apart hub headers 164 in fluid communication with the compressionchamber inlet ports 160. Referring to FIG. 3 , each hub header 164extends along a hub header centerline 165 between a hub header first end164 a open to the hub body first endface 150 a for receiving the firstfluid, and a hub header second end 164 b spaced axially apart from thehub header first end 164 a toward the hub body second endface 150 b (seealso FIGS. 2B and 4B).

Referring to FIG. 4B, in the example illustrated, the header centerline165 extends helically about the drive axis 104 in the circumferentialforward direction 112 from the header first end 164 a to the headersecond end 164 b. Referring to FIG. 2B, each header 164 has a crosssectional area perpendicular to the drive axis 104. In the exampleillustrated, the cross-sectional area of each header 164 decreases alongthe header centerline 165 from the header first end 164 a toward theheader second end 164 b.

Referring still to FIG. 2B, in the example illustrated, the hub manifold128 includes a plurality of hub aerodynamic features 134 (see also FIG.8 ) extending at least partially across the header first ends 164 a andfixed to rotate with the hub body 150 for conditioning flow of the firstfluid entering the header first ends 164 a. In the example illustrated,the aerodynamic features 134 comprise hub airfoils 136. In the exampleillustrated, the hub airfoils 136 are spaced circumferentially apartfrom one another about the drive axis 104 and extend radially acrossrespective header first ends 164 a (see also FIG. 8 ).

Referring to FIG. 3 , in the example illustrated, the compressionchamber inlet ductwork 130 includes a plurality of hub first conduits166 (also referred to as hub inlet conduits 166) for conducting thefirst fluid from the hub headers 164 to the compression chamber inletports 160. Referring to FIG. 4B, each hub inlet conduit 166 extendsalong a hub inlet conduit centerline 167 between a respectivecompression chamber inlet port 160 and a hub first conduit end 166 a(also referred to as a hub inlet conduit intake end 166 a) open to arespective hub header 164.

In the example illustrated, the hub inlet conduit centerline 167 curvescircumferentially between the compression chamber inlet port 160 and thehub first conduit end 166 a. In the example illustrated, the inletconduit centerline 167 extends from the inlet conduit intake end 166 ato the compression chamber inlet port 160 in a circumferential seconddirection (also referred to as a reverse direction) opposite the forwarddirection 112 for directing fluid passing radially outwardly through theinlet conduit 166 in the reverse direction. This can help provide aninflow velocity of the first fluid corresponding to the developed flowfield in the radially inner portion of the compression chambers 120, andmay help improve compression efficiency.

Referring to FIG. 3 , in the example illustrated, a second-fluidevacuation space 170 is provided in the casing 102 for receiving thesecond fluid discharged from the hub manifold 128, and evacuating thesecond fluid from the casing 102. In the example illustrated, thesecond-fluid evacuation space 170 is provided in the hub manifold bore156.

In the example illustrated, the turbine chamber outlet ductwork 132includes a plurality of hub second conduits 168 (also referred to as huboutlet conduits 168) for conducting the second fluid from the turbinechamber outlet ports 162 to the second-fluid evacuation space 170.Referring to FIG. 5B, in the example illustrated, each outlet conduit168 extends along a hub second conduit centerline 169 (also referred toas a hub outlet conduit centerline 169) between a respective turbinechamber outlet port 162 and a hub second conduit end 169 a (alsoreferred to as a hub outlet conduit discharge end 169 a). The hub outletconduit discharge end 169 a is open to the hub body inner surface 154(and the hub manifold bore 156, see FIG. 3 ) and is in fluidcommunication with the evacuation space 170.

In the example illustrated, the hub outlet conduit centerline 169 curvescircumferentially between the turbine chamber outlet port 162 and thehub second conduit end 169 a. In the example illustrated, the outletconduit centerline 169 extends from the turbine chamber outlet port 162to the outlet conduit discharge end 169 a in the circumferential forwarddirection 112 for directing the second fluid passing radially inwardlythrough the hub outlet conduit 168 in the forward direction 112. Thiscan help provide an outlet curvature having an intake portioncorresponding to the developed flow field in the radially inner portionof the turbine chambers.

Referring to FIG. 3 , the second fluid can be evacuated through thesecond-fluid evacuation space 170 in an axial direction. In the exampleillustrated, the second fluid is evacuated through the evacuation space170 in the axially forward direction.

Referring still to FIG. 3 , in the example illustrated, the shaft 110includes a shaft body 172 in the hub manifold bore 156, and a shaft bore174 in the shaft body 172 coaxial with the drive axis 104. In theexample illustrated, the shaft bore 174 comprises the second-fluidevacuation space 170. In the example illustrated, the shaft 110 includesa plurality of shaft ports 176 extending radially through the shaft body172 and between respective hub outlet conduits 168 and the second-fluidevacuation space 170 for conducting the second fluid from the outletconduits 168 to the evacuation space 170.

In the example illustrated, at least a portion of the hub body 150 isformed of a thermally conductive material for conductively transferringheat between the first fluid passing through the compression chamberinlet ductwork 130 and the second fluid passing through the turbinechamber outlet ductwork 132.

Referring to FIG. 2 , in the example illustrated, the shroud manifold138 is fixed to rotate with the shaft 110 about the drive axis 104, andforms part of the rotor assembly of the drive 100. Referring to FIG. 3 ,the shroud manifold 138 includes a shroud body 180 coaxial with thedrive axis 104, and each of the turbine chamber inlet ductwork 140 andthe compression chamber outlet ductwork 142 is internal the shroud body180.

In the example illustrated, the shroud body 180 is generallycylindrical. The shroud body 180 includes a shroud body first endface180 a, and a shroud body second endface 180 b axially opposite theshroud body first endface 180 a (see also FIGS. 2A and 2C). In theexample illustrated, the shroud body first endface 180 a is locatedtoward the casing rear end 108, and the shroud body second endface 180 bis spaced apart from the shroud body first endface 180 a toward thecasing front end 106.

In the example illustrated, the shroud body 180 includes a shroud bodyinner surface 184 directed radially inwardly toward the disc pack 114and extending axially between the first and second endfaces 180 a, 180b. In the example illustrated, the shroud body 180 includes a radiallyoutwardly directed shroud body outer surface 182 radially opposite theshroud body inner surface 184 and extending axially between the shroudbody first and second endfaces 180 a, 180 b. In the example illustrated,the shroud manifold 138 includes a shroud manifold bore 186 in theshroud body 180 coaxial with the drive axis 104, and bounded radially bythe shroud body inner surface 184. The shroud manifold bore 186 is sizedto receive the disc pack 114 therein, and the disc spaces 118 arebounded radially by the shroud body inner surface 184.

In the example illustrated, the turbine chamber inlet ductwork 140includes a plurality of shroud first ports 190 (also referred to asturbine chamber inlet ports 190) open to the shroud body inner surface184 for discharging the second fluid from the turbine chamber inletductwork 140 and into the turbine chambers 122 to urge rotation of thedisc pack 114 in the forward direction 112. In the example illustrated,the compression chamber outlet ductwork 142 includes a plurality ofshroud second ports 192 (also referred to as compression chamber outletports 192) open to the body inner surface 184 for evacuating the firstfluid from the compression chambers 120 and into the compression chamberoutlet ductwork 142.

Referring to FIG. 2C, in the example illustrated, the plurality ofturbine chamber inlet ports 190 are arranged in axially spaced apartshroud first sets 190 a (also referred to as shroud inlet sets 190 a),with each set 190 a of turbine chamber inlet ports 190 open to arespective turbine chamber 122. In the example illustrated, theplurality of compression chamber outlet ports 192 are arranged inaxially spaced apart shroud second sets 192 a (also referred to asshroud outlet sets 192 a), with each set of compression chamber outletports 192 open to a respective compression chamber 120. In the exampleillustrated, the shroud inlet sets 190 a alternate axially with theshroud outlet sets 192 a.

Referring to FIG. 5A, in the example illustrated, the turbine chamberinlet ports 190 in each set 190 a are spaced circumferentially apartfrom one another about the drive axis 104. In the example illustrated,the turbine chamber inlet ports 190 in each set 190 a lie in a commonshroud first plane 193 a oriented normal to the drive axis 104. In theexample illustrated, each shroud first plane 193 a is coincident with arespective hub second plane 163 b, and the turbine chamber inlet ports190 open to a respective turbine chamber 122 are generally in axialalignment with the turbine chamber outlet ports 162 open to that sameturbine chamber 122.

Referring to FIG. 4A, in the example illustrated, the compressionchamber outlet ports 192 in each set 192 a are spaced circumferentiallyapart from one another about the drive axis 104. In the exampleillustrated, the compression chamber outlet ports 192 in each set 192 alie in a common shroud second plane 193 b oriented normal to the driveaxis. In the example illustrated, each shroud second plane 193 b iscoincident with a respective hub first plane 163 a, and the compressionchamber outlet ports 192 open to a respective compression chamber 120are generally in axial alignment with the compression chamber inletports 160 open to that same compression chamber 120.

Referring to FIG. 3 , in the example illustrated, the turbine chamberinlet ductwork 140 includes a plurality of circumferentially spacedapart shroud headers 194 in fluid communication with the turbine chamberinlet ports 190 (see also FIG. 5A). Each shroud header 194 extends alonga shroud header centerline 195 between a shroud header first end 194 aopen to the shroud body first endface 180 a for receiving the secondfluid and a shroud header second end 194 b spaced axially apart from theshroud header first end 194 a toward the shroud body second endface 180b. In the example illustrated, the shroud header centerline 195 extendsgenerally parallel to the drive axis 104.

Referring to FIG. 2C, in the example illustrated, the shroud manifold138 includes a plurality of shroud aerodynamic features 144 extending atleast partially across the shroud header first ends 194 a and fixed torotate with the shroud body 180 for conditioning flow of the secondfluid entering the shroud headers 194. Referring to FIG. 5A, in theexample illustrated, the shroud aerodynamic features 144 comprise shroudairfoils 146. The shroud airfoils 146 are spaced circumferentially apartfrom one another about the drive axis 104 and extend radially acrossrespective shroud header first ends 194 a.

Referring to FIG. 3 , in the example illustrated, the turbine chamberinlet ductwork 140 includes a plurality of shroud first conduits 196(also referred to as shroud inlet conduits 196) for conducting thesecond fluid from the shroud headers 194 to the turbine chamber inletports 190. Referring to FIG. 5A, each shroud inlet conduit 196 extendsalong a shroud first conduit centerline 197 (also referred to as shroudinlet conduit centerline 197) between a respective turbine chamber inletport 190 and a shroud first conduit end 196 a (also referred to as ashroud inlet conduit intake end 196 a) open to a respective shroudheader 194.

In the example illustrated, the shroud inlet conduit centerline 197curves circumferentially between the turbine chamber inlet port 190 andthe shroud inlet conduit intake end 196 a. In the example illustrated,the shroud inlet conduit centerline 197 extends from the inlet conduitintake end 196 a to the turbine chamber inlet port 190 in thecircumferential forward direction 112 for directing fluid passingradially inwardly through the shroud inlet conduit 196 and into arespective turbine chamber 122 in the forward direction 112 to urgerotation of the disc pack 114.

Referring to FIG. 3 , in the example illustrated, a first-fluidevacuation space 178 is provided in the casing 102 for receiving thefirst fluid discharged from the shroud manifold 138, and evacuating thefirst fluid from the casing 102. In the example illustrated, thefirst-fluid evacuation space 178 is radially intermediate the shroudmanifold 138 and an inner surface 103 of the casing 102. In the exampleillustrated, the first-fluid evacuation space 178 is bounded radially bythe shroud body outer surface 182. The first fluid can be evacuatedthrough the first-fluid evacuation space 178 in an axial direction. Inthe example illustrated, the second fluid is evacuated through theevacuation space 178 in the axially rearward direction. In someexamples, the first-fluid evacuation space 178 can comprise a vanelessspace open to a semi-vaneless space in the casing for facilitatingdiffusion of the first fluid.

Referring still to FIG. 3 , in the example illustrated, the compressionchamber outlet ductwork 142 includes a plurality of shroud secondconduits 198 (also referred to as shroud outlet conduits 198) forconducting the first fluid from the compression chamber outlet ports 192to the first-fluid evacuation space 178. Referring to FIG. 4A, eachoutlet conduit 198 extends along a shroud outlet conduit centerline 199between a respective compression chamber outlet port 192 and a shroudsecond conduit end 198 a (also referred to as a shroud outlet conduitdischarge end 198 a) open to the shroud body outer surface 182 and influid communication with the first-fluid evacuation space 178. In theexample illustrated, the shroud outlet conduit centerline 199 curvescircumferentially between the chamber outlet port 192 and the shroudoutlet conduit discharge end 198 a.

In the example illustrated, the shroud outlet conduit 198 includes anintake portion 200 extending along an intake portion centerline 201 fromthe compression chamber outlet port 192 toward the outlet conduitdischarge end 198 a. In the example illustrated, the intake portioncenterline 201 curves circumferentially from the compression chamberoutlet port 192 toward the outlet conduit discharge end 198 a. In theexample illustrated, the intake portion centerline 201 extends from thecompression chamber outlet port 192 toward the outlet conduit dischargeend 198 a in the circumferential reverse direction (opposite the forwarddirection 112) for directing the first fluid entering and passingradially outwardly through the intake portion 200 in the reversedirection. This can help accommodate the developed flow field in theradially outer portion of the compression chambers.

In the example illustrated, the shroud outlet conduit 198 includes adischarge portion 202 extending along a discharge portion centerline 203from the intake portion 200 to the outlet conduit discharge end 198 a.In the example illustrated, the discharge portion centerline 203 curvescircumferentially from the intake portion 200 to the outlet conduitdischarge end 198 a. The discharge centerline 203 and the intake portioncenterline 201 can curve in circumferentially opposite directions.

In the example illustrated, the discharge portion centerline 203 canextend from the intake portion 200 to the outlet conduit discharge end198 a in one of the circumferential forward direction 112 and thereverse direction for directing the first fluid passing radiallyoutwardly through the discharge portion 202 and into the evacuationspace 178 in the one of the forward direction 112 and the reversedirection. In the example illustrated, the discharge portion centerline203 extends from the intake portion 200 to the outlet conduit dischargeend 198 a in the circumferential forward direction 112 for directing thefirst fluid passing radially outwardly through the discharge portion 202and into the evacuation space 178 in the forward direction 112. This canhelp machine performance.

The drive 100 can include one or more disc mounting features. The discmounting features can, for example, facilitate axial positioning of thediscs 116 and/or rotational locking of the disc pack 114 with one orboth of the hub manifold 128 and the shroud manifold 138. The discmounting features can include, for example, weldments, keys, keyways,and/or spacers. In some examples, the disc pack can be bonded (e.g.welded or adhered) to one or both of the hub manifold body and theshroud manifold body to rotationally lock the disc pack 114 thereto.

Referring to FIG. 2C, in the example illustrated, the disc mountingfeatures include a plurality of axially spaced apart circumferentialshroud grooves 204 in the shroud body inner surface 184. Each shroudgroove 204 is axially intermediate a respective shroud inlet set 190 aof turbine chamber inlet ports 190, and a respective axially adjacentshroud outlet set 192 a of compression chamber outlet ports 192. In theexample illustrated, each shroud groove 204 receives a radially outerperipheral edge of a respective disc 116 to facilitate axial positioningof the discs 116.

Referring to FIG. 6C, in the example illustrated, the disc mountingfeature further includes a plurality of axially spaced apartcircumferential hub grooves 205 (shown schematically in FIG. 6C-see alsogrooves 1205 in FIGS. 9A and 9B) in the hub body outer surface 152. Eachhub groove 205 is axially intermediate a respective hub inlet set 160 aof compression chamber inlet ports 160 and a respective axially adjacenthub outlet set 162 a of turbine chamber outlet ports 162. Each hubgroove 205 can receive a radially inner peripheral edge of a respectivedisc 116 to facilitate axial positioning of the discs. In the exampleillustrated, the shroud and hub grooves 204, 205 are in axial alignmentwith one another.

The discs 116 can be positioned into the shroud grooves 204 through, forexample, thermal expansion of the shroud body 180 relative to the discs116 and/or thermal contraction of the discs 116 relative to the shroudbody 180. The discs 116 can be positioned into the hub grooves 205through, for example, thermal contraction of the hub body 150 relativeto the discs 116 and/or thermal expansion of the discs 116 relative tothe hub body 150.

In some examples, the disc mounting feature includes an interferencestructure for engagement with the disc pack 114 to rotationally lock thedisc pack 114 with one or both of the hub manifold 128 and the shroudmanifold 138. The interference structure can comprise, for example,axially facing groove surfaces of the shroud grooves 204 and/or the hubgrooves 205 for providing an interference fit with the discs 116. Insome examples, the interference structure can include, for example,protrusions, pins, and/or keys for engagement with correspondingrecesses, apertures, and/or keyways in one or more discs 116 torotationally lock the disc pack 114 with one or both of the hub manifold128 and the shroud manifold 138.

Referring to FIG. 8 , in the example illustrated, the hub body 150includes a core 206 coaxial with the drive axis 104 and through which atleast a portion of the compression chamber inlet ductwork 130 and theturbine chamber outlet ductwork 132 passes. In the example illustrated,the hub headers 164, hub inlet conduits 166, and hub outlet conduits 168pass through the core 206 (see also FIG. 4B).

Referring still to FIG. 8 , in the example illustrated, the core 206 isof integral, unitary, one-piece construction. The core 206 can be formedusing, for example, a 3D printing or casting process which can helpprovide for complex ductwork geometry internal the core 206. In somecases, components formed using such processes may have limitedstructural integrity and/or material properties that may be less thanideal for rotary applications involving high rotational and/or thermalstresses. In the example illustrated, the hub body 150 includes a frame208 mounted to the core 206 for exerting an inwardly directed force onthe core 206 to regulate a stress distribution therein during operation(see also FIGS. 6A and 6B). This can help improve, for example, theoperating range and/or life expectancy of the core 206.

Referring to FIG. 8 , in the example illustrated, the core 206 has aradially outwardly directed core outer surface 210, and the frame 208includes an outer sleeve 212 mounted over the core 206 and in engagementwith the core outer surface 210 for inducing radial compression of thecore 206 during operation. In the example illustrated, the outer sleeve212 comprises the hub body outer surface 152. In some examples, theouter sleeve 212 can induce radial compression through, for example, aninterference fit with the core outer surface 210, and/or through aclamping assembly.

In the example illustrated, the frame 208 includes a plurality ofanchors 214. Each anchor 214 extends between an anchor outer end 214 afixed to the outer sleeve 212 and an anchor inner end 214 b fixed to theshaft 110 for inducing radial compression of the core 206. In theexample illustrated, the hub body 150 includes a plurality of apertures216 passing radially through the core 206, and the anchors 214 extendthrough respective apertures 216. This can facilitate alignment betweenthe ductwork portions passing through the outer sleeve 212 and theductwork portions internal the core 206, and between the shaft ports 176and the ductwork portions internal the core 206.

Referring to FIGS. 2B and 2D, in the example illustrated, the core 206has a core first endface 206 a and a core second endface 206 b axiallyopposite the core first endface 206 a. The frame 208 includes a firstend cap 218 a in engagement with the core first endface 206 a, and asecond end cap 218 b in engagement with the core second endface 206 b.The first and second end caps 218 a, 218 b can be anchored to oneanother for inducing axial compression of the core 206 during operation.In the example illustrated, the first and second end caps 218 a, 218 bare anchored to one another via the outer sleeve 212.

Referring to FIG. 2D, in the example illustrated, each of the first andsecond endcaps 218 a, 218 b has a radially outer endcap portion 220fixed to the outer sleeve 212 and the disc pack 114, a radially innerendcap portion 222 fixed to the shaft 110, and a radially intermediateendcap portion 224 connecting the radially outer endcap portion 220 andthe radially inner endcap portion 222.

In the example illustrated, torque load between the disc pack 114 andthe shaft 110 is transferred through the frame 208. This can help reducetorque load transfer through the core 206, which may help improve theoperating range and/or life expectancy of the core 206. In the exampleillustrated, the frame 208 includes a disc pack mounting portion 226 forengagement with the disc pack 114 to fix the disc pack to the hub body150. The disc pack mounting portion 226 can include the outer sleeve212, and/or the radially outer endcap portions 220.

In the example illustrated, the frame 208 includes a shaft mountingportion 228 for engagement with the shaft 110 to fix the shaft 110 tothe frame 208. The shaft mounting portion 228 is spaced radiallyinwardly apart from the disc pack mounting portion 226. In the exampleillustrated, the shaft mounting portion 228 includes the radially innerendcap portions 222.

In the example illustrated, the frame 208 includes one or moretorque-transfer members 230 for transferring torque between the discpack mounting portion 226 and the shaft mounting portion 228. Referringto FIG. 2D, each torque-transfer member 230 has a radially outer end 230a fixed to the disc pack mounting portion 226 and a radially inner end230 b fixed to the shaft mounting portion 228. In the exampleillustrated, the torque-transfer members 230 include the radiallyintermediate endcap portions 224.

Referring to FIG. 8 , in the example illustrated, hub aerodynamicfeatures 134 are mounted to the frame 208.

Referring to FIGS. 9A-9B, an example of another hub manifold 1128 for arotor assembly of a cohesion-type drive is illustrated. The manifold1128 has similarities to the hub manifold 128, and like features areidentified by like reference characters, incremented by 1000.

In the example illustrated, the manifold 1128 includes a manifold body1150 extending along a drive axis 1104 for rotation thereabout. The body1150 includes a first endface 1150 a, a second endface axially oppositethe first endface 1150 a, and a radially outwardly directed body outersurface 1152 extending between the first and second endfaces 1150 a,1150 b. In the example illustrated, the body is of integral, unitary,one-piece construction. In the example illustrated, the hub manifoldincludes a plurality of grooves 1205 in the body outer surface 1152 forreceiving radially inner peripheral edges of discs of the drive tofacilitate mounting of the discs.

Referring to FIG. 10 , another example of a cohesion-type drive 2100 isillustrated schematically. The cohesion-type drive 2100 has similaritiesto the drive 100, and like features are identified by like referencecharacters, incremented by 2000. In the example illustrated, the drive2100 includes a hub manifold 2128 having a manifold body 2150 extendingalong a drive axis 2104 for rotation thereabout. The body 2150 includesa first endface 2150 a, a second endface 2150 b axially opposite thefirst endface 2150 a, a radially outwardly directed outer surface 2152extending between the first and second endfaces 2150 a, 2150 b, and aradially inwardly directly inner surface 2154 radially opposite theouter surface 2152.

In the example illustrated, the body 2150 is tapered radially along thedrive axis 2104. This can allow for a variation in an inner radius ofthe first and second working chambers 2120, 2122 along the drive axis2104, and can facilitate optimization of, for example, mass flow andwork. In the example illustrated, the outer surface 2152 is spacedradially apart from the drive axis by a body outer radius 2232. In theexample illustrated, the body outer radius 2232 decreases along thedrive axis 2104 from the first endface 2150 a toward the second endface2150 b of the body 2150. In the example illustrated, the inner surface2154 is spaced radially apart from the drive axis 2104 by a body innerradius 2234. In the example illustrated, the body inner radius 2234decreases along the drive axis 2104 from the first endface 2150 a towardthe second endface 2150 b of the body 2150.

Referring to FIG. 11 , an example of another manifold 3128 for a rotorassembly of a cohesion-type drive is illustrated schematically. Themanifold 3128 has similarities to the hub manifold 128, and like featureare identified by like reference characters, incremented by 3000.

In the example illustrated, the manifold 3128 includes a manifold body3150 extending along a drive axis 3104 for rotation thereabout. The body3150 includes a core 3206 coaxial with the drive axis 3104, and a frame3208 mounted to the core 3206 for exerting an inwardly directed force onthe core 3206 to regulate a stress distribution therein during operationof the drive. The manifold body 3150 includes ductwork internal the body3150 for fluid communication with a plurality of working chambers of thedrive. At least a portion of the ductwork passes through the core 3206.

In the example illustrated, the core 3206 has a radially outwardlydirected core outer surface 3210, and the frame 3208 includes an outersleeve 3212 mounted over the core 3206 and in engagement with the coreouter surface 3210 for inducing radial compression of the core 3206during operation.

In the example illustrated, the body 3150 includes a core bore 3238 inthe core 3206 coaxial with the drive axis 3104 and bounded by a radiallyinwardly directed core inner surface 3239 of the core 3206. In theexample illustrated, the frame 3208 includes an inner sleeve 3240 in thecore bore 3238 and in engagement with the core inner surface 3239. Inthe example illustrated, the outer and inner sleeves 3212, 3240 areanchored to one another for inducing radial compression of the core 3206during operation. In the example illustrated, the outer sleeve 3212comprises a body outer surface 3152 of the manifold body 3150, and theinner sleeve 3240 comprises a body inner surface 3154 of the manifoldbody 3150.

In the example illustrated, the frame 3208 includes a plurality ofanchors 3214 anchoring the outer and inner sleeves 3212, 3240 to oneanother. Each anchor 3214 extends between an anchor outer end 3214 afixed to the outer sleeve 3212 and an anchor inner end 3214 b fixed tothe inner sleeve 3240. In the example illustrated, the anchor outer ends3214 a are axially offset from the anchor inner ends 3214 b. In theexample illustrated, the manifold body 3150 includes a plurality ofapertures passing radially through the core 3206 between the core outerand inner surfaces 3210, 3239, and the anchors extend through respectiveapertures.

In the example illustrated, the core 3206 has a core first endface 3206a and a core second endface 3206 b axially opposite the core firstendface 3206 a. In the example illustrated, the frame 3208 includes afirst end cap 3218 a in engagement with the core first endface 3206 aand a second end cap 3218 b in engagement with the core second endface3206 b. The first and second end caps 3218 a, 3218 b are anchored to oneanother for inducing axial compression of the core 3206 duringoperation. In the example illustrated, the first and second end caps3218 a, 3218 b are anchored to one another via the outer and innersleeves 3212, 3240.

In the example illustrated, torque load between a disc pack 3114 and ashaft 3110 is transferred through the frame 3208. In the exampleillustrated, the frame 3208 includes a disc pack mounting portion 3226for engagement with the disc pack 3114 to fix the disc pack to the frame3208. The disc pack mounting portion 3226 can include the outer sleeve3212, and/or radially outer endcap portions.

In the example illustrated, the frame 3208 includes a shaft mountingportion 3228 for engagement with the shaft 3110 to fix the shaft 3110 tothe frame 3208. The shaft mounting portion 3228 is spaced radiallyinwardly from the disc pack mounting portion 3226. The shaft mountingportion 3228 can include the inner sleeve 3240 and/or radially innerendcap portions.

In the example illustrated, the frame 3208 includes one or moretorque-transfer members 3230 for transferring torque between the discpack mounting portion 3226 and the shaft mounting portion 3228. Eachtorque-transfer member 3230 has a radially outer end 3230 a fixed to thedisc pack mounting portion 3226 and a radially inner end 3230 b fixed tothe shaft mounting portion 3228. In the example illustrated, thetorque-transfer members 3230 include radially intermediate endcapportions 3224.

Referring to FIG. 12 , charts A-D show the difference in stressdistribution for a hollow rotating disc with and without imposed radialloads at the inner and outer radiuses. The charts A-D show radial, hoop,and shear stress distribution in the rotating disc for the fourdifferent boundary conditions outlined in Table 1 of FIG. 12 . Thestresses are radial and normalized by a factor of (ρω²)/8, with apositive stress indicating a tensile load. Radial and hoop stresses areshown in solid lines, and shear stress is shown in dashed lines.

These charts demonstrate how pre-stressing a hollow rotating disc, suchas, for example, the core 3206, may help reduce maximum shear stressunder loading. This may improve the range of operation or lifeexpectancy such components, and may also allow for control of the stressdistribution throughout through variation in the boundary conditions,which may be helpful in cases where the components are of limitedstructural integrity.

1-18. (canceled)
 19. A rotary manifold for a cohesion-type drive,comprising: a) a manifold body extending along a drive axis for rotationabout the drive axis, the body including a core coaxial with the driveaxis, and a frame mounted to the core for exerting an inwardly directedforce on the core to regulate a stress distribution therein duringoperation of the drive; and b) ductwork internal the body for fluidcommunication with a plurality of working chambers of the drive, atleast a portion of the ductwork passing through the core.
 20. The rotarymanifold of claim 19, wherein the core has a radially outer surface, andthe frame includes an outer sleeve mounted over the core in engagementwith the radially outer surface for inducing radial compression of thecore during operation. 21-25. (canceled)
 26. The rotary manifold ofclaim 20, wherein the ductwork includes a plurality of conduitsextending through the core, each conduit open to the radially outersurface for fluid communication with a respective working chamber of theplurality of working chambers through a respective opening in the outersleeve.
 27. The rotary manifold of claim 19, wherein the ductwork passesthrough the frame for fluid communication with the plurality of workingchambers.
 28. The rotary manifold of claim 19, wherein the core is ofintegral, unitary, one-piece construction.
 29. The rotary manifold ofclaim 19, wherein the core is formed through an additive manufacturingprocess.
 30. The rotary manifold of claim 19, wherein the plurality ofworking chambers are defined by a disc pack mountable to the manifoldbody and include a plurality of first chambers and a plurality of secondchambers alternating axially with and in fluid isolation of theplurality of first chambers, and wherein the ductwork comprises a firstductwork for fluid communication with the plurality of first chambersand a second ductwork for fluid communication with the plurality ofsecond chambers, the second ductwork in fluid isolation of the firstductwork within the manifold body.
 31. A rotary manifold for acohesion-type drive having a disc pack defining a plurality of firstworking chambers and a plurality of second working chambers axiallyinterspersed between and in fluid isolation of the plurality of firstworking chambers, the rotary manifold comprising: a) a manifold body forengagement with a radial periphery of the disc pack, the manifold bodyextending along and rotatable about a drive axis, and the manifold bodyincluding a core coaxial with the drive axis and a frame mountedradially over the core for compressive engagement therewith to regulatea stress distribution in the core during operation of the cohesion-typedrive; b) a first ductwork internal the manifold body and passingthrough the core and the frame for fluid communication with theplurality of first working chambers; and c) a second ductwork internalthe manifold body and in fluid isolation of the first ductwork, thesecond ductwork passing through the core and the frame for fluidcommunication with the plurality of second working chambers.
 32. Therotary manifold of claim 31, wherein the frame comprises an outer sleevemounted over a radially outer surface of the core.
 33. The rotarymanifold of claim 31, wherein the first ductwork comprises a pluralityof headers extending along and spaced apart from each other about thedrive axis, each header of the plurality of headers open to theplurality of first working chambers through respective ports in themanifold body.
 34. The rotary manifold of claim 31, wherein the secondductwork comprises a plurality of conduits, each conduit extendingradially through the manifold body between a respective second workingchamber of the plurality of second working chambers and a fluidevacuation space extending along the drive axis radially opposite theplurality of second working chambers.
 35. The rotary manifold of claim31, wherein the core is of integral, unitary, one-piece construction 36.The rotary manifold of claim 31, wherein core is formed through anadditive manufacturing process.